SUMMARY DIGEST DEPLOYMENT PROCEDURES · value of 28, 000 lbm* was used as nominal delivery...

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION OFFICE OF MANNED SPACE FLIGHT

DEPARTMENT OF THE ARMY OFFICE OF THE CHIEF OF ENGINEERS

SUMMARY DIGEST

DEPLOYMENT PROCEDURES LUNAR EXPLORATION SYSTEMS FOR APOLLO

MISSILES & SPACE COMPAN Y A GROUP DIVISION OF LOCKHEED AIRCRAFT CORPORAT I ON

SUNNYVALE, CALIFORNIA

LMSC -665606

STUDY OF DEPLOYMENT PROCEDURES

FOR

LUNAR EXPLORATION SYSTEMS FOR APOLLO (LESA)

Contract DA -49-129-ENG-534

FINAL REPORT

SUMMARY DIGEST

Prepared by

LOCKHEED MISSILES & SPACE COMPANY Sunnyvale, California

A Group Division of Lockheed Aircraft Corporation

Prepared for

Department of the Army Office of the Chief of Engineers

Washington, D. C.

and

National Aeronautics and Space Administration Office of Manned Space Flight

Washington, D. C.

15 February 19 65

LMSC-665606

NAME

Lockheed Missiles & Space Co.

Holmes & Narver, Inc. , Advanced Technology Group

Clark Equipment Company, Development Division

Professors C. H. Oglesby and H. W. Parker, Stanford University, College of Engineering Department of Civil Engineering

Bendix Systems Division

STUDY TEAM

FUNCTION

Prime Contract Management and Direction Systems Integration Structures Design

Foundation Design, Operation Studies, and Procedure Development

Conceptual Design of Materials-Handling and Deployment Equipment

Consultants to Holmes and Narver on Construction Methods

Consultants on Lunar Surface Mobility

ii

LOCKHEED MISSILES Be SPACE COMPANY

FOREWORD

This booklet is a brief summary of the final report for the six-month

study of Deployment Procedures for Lunar Exploration Systems for

Apollo (LESA) that began on 29 June 1964. This study constitutes a

part of the National Aeronautics and Space Administration concept

development program for LESA and was conducted under contract

DA-94-129-ENG-534 with the Office of the Chief of Engineers, Depart

ment of the Army.

Details not included in this Summary Digest can be found in the follow

ing volumes of the final report:

Volume I - SUMMARY

Volume II -TECHNICAL DISCUSSION

Volume III - APPENDIX

iii

LOCKHEED MISSILES & SPACE COMPANY

CONTENTS

Section Page

STUDY TEAM ii

FOREWORD iii

1 INTRODUCTION 1

2 PRIMARY RESTRAINTS 2

3 LESA BASE MODULES 5

4 DEPLOYMENT OPERATIONS 6

4.1 Preparatory Operations 6

4.2 Unloading Operations 8

4.3 Soil Operations 8

4.4 Transportation Operations 8

4.5 Emplacement and Erection Operations 12

5 DEPLOYMENT PROCEDURES 12

6 DEPLOYMENT EQUIPMENT 14

7 STRUCTURES DESIGN 14

7.1 Basic Shelter Concept 17

7. 2 Payload Packaging 19

8 CONCLUSIONS AND RECOMMENDATIONS 19

8.1 Conclusions 19

8.2 Recommendations 23

GLOSSARY G-1

iv


Section 1

INTRODUCTION

The objective of this study is to analyze procedures, equipment concepts, and structures

design concepts for deployment of exploration systems on the surface of the moon. The

study constitutes a part of the National Aeronautics and Space Administration concept

development program for Lunar Exploration Systems for Apollo (LESA) and was con

ducted under contract with the Office of the Chief of Engineers, Department of the Army.

The LESA concept is a system of one or more lunar bases from which missions of

scientific interest would originate. These bases would be composed of a system of

modular base elements, grouped in various payload packages, launched to the moon by

the Saturn V booster, and landed with the aid of a cryogen-fueled lunar landing vehicle

(LLV). Because of the undetermined aspects of the lunar exploration program (required

missions, lunar environment, exploration funding, relative importance of various

exploration methods), the following spectrum of LESA base models, each with specified

crew levels and mission durations, was examined:

Base Model

1

2

3

4

Crew Size (men)

3

6

12

18

Base Duration (months)

3

6

12+

24+

For purposes of this study, a deployment procedure is a complete specification of one

scheme for deploying a LESA base model, including the identification of deployed

modules, sequence of events, and required equipment. A deployment operation is a

major identifiable portion of a deployment procedure (e.g. , shelter unloading, shelter

1


transportation, soil collection). A deployment task is a detailed part of an operation

determined after a method of performing the operation has beeri selected.

Figure 1 presents the information flow plan used in this study. The primary study

task was the development of construction procedures, equipment concepts, and se

quence of events. To accomplish this, lunar environment models and surface charac

teristics were defined, base module concepts determined, and relationships between

man and machine formulated. Then, the major operations required to deploy each base

model were determined. A broad range of methods for performing the various deploy

ment operations was evaluated, and the most promising method for each operation was

selected by means of a combination of logical analysis and a specially developed cost

point evaluation system.

A sequence of tasks required to accomplish each selected method of operation was then

formulated. A method of performing each task was selected considering crew capability,

time required, and feasible equipment characteristics.

Thus, with detailed knowledge of the method of performing each operation, various

operations could be integrated into alternate deployment procedures in order to examine

the influence of deployment variables (such as lunar soil characteristics, base module

clustering, and base module offloading) on the establishment of LESA bases.

Section 2

PRIMARY RESTRAINTS

Before the LESA deployment operations could be evaluated, certain restraints on

deployment activity were evaluated. Assumptions were made on the lunar environment

based on a review of current literature. Selenomorphic models were defined as shown

in Table A. Soil Model 1 represents a site on one of the lunar maria, which are pre

sumed to be covered by a lava-like substance that has been well churned up by particle

2


PERFORM DETAILED

r 0 () :A :r 1"1 1"1

• MA TERIA.LS SELECTKJN CONCEPT DESIGNS

e BASE ELEMENT CONFIGURA 'MONS DEFINE AND ANALYZE

AND ANALY518 OF

f J-- FOUNDA. TDN CONCEPTS

f----eo BASE STRUCTURES • STRUCTIJRE CONCEPTS

PERFORM PRELIMINARY REVIEW AND CONCEPT DESIGN OF • p,apo.e, requirement.

• Shelter e FOUNDATION CONCEPTS

SELECT STRUCTURAL BASE STRUCTURES

• Weight, eo~;t, operatiaa..., • Sul»tructurll•

e TECHNOLOGICAL PROBLEMS

MATERIALS

UMful Ute, malntllnmoe e Auxtltary •tructure

1 l 0 • PREFERRED CONSTRUCTION DEVELOP CONS'm:UCTION

PROCEDURES PROCEDURES, SYSTEMS AND

3: e SEQUENCE OF EVENTS

SEQUENCE OF EVENTS FOR EACH BASE MODEL

e BASE BUILDUP SCHEDULE • Perform certain

(/) (/)

r 1"1

• PACKAGED PAYLOAD trn.deQH studies CONFIGURATIONS I J

• Prelimlnnry ~~ehedule• • MANPOWER REQUIREMENTS

DEFINE LUNAR REVIEW LUNAR I J DEFINE OPERATIONS

• Det:aJled tuk perform-• EFFECTS OF LUNAR SURFACE

SURFACE, SOIL, AND BASE CONCEPT I FOR BASE CONSTRUCTION

arteearualy•i• AND ENYmONMENT MODELS

ENVIRONMENT MODELS ,.... • Effecta of aurface and • EXPENDABLE MATERIAL envtroftment modet.

(/) C;.:i • Select preferred procedunla REQuntEMENTS

~

(/) 1J )> 0 1"1

0 0 3: 1J )>

• CONSTRUCTION COSTS • DeW led logistic• and con-• CONSTRUCTION TRAINING l! atruction analyats

DEMONSTRA 110N PROORAM

1 ' • MATERIA 1.8 HANDLING I DEFINE HANDLING

AND DEPLOYMENT EQUIPMENT REQUIREMF.NTS EQUIPMENT INTEGRA nlN EQUIPMENT CONCEPTS EVALUATE OPERATION

• Integration of devices with • WEIGHTS, DIMENSKJNS PERFORMANCE METHODS

I DEF1NE MAN-MACHINE 1 -roprla"' platform•

• CHECKf>UT PROCEDURES

rn'TERFACES • Categorize I-• Equipment s:torage and

• R l! D, AND PRODUCTION

• EnVironment reatraintll • Compare checkout requiremenb

SCHEDULES AND COSTS • Human Umltll • Eliminate

• Packaging requirements: • TECHNOUXHCAL PROBLEMS • Define coutrain~ I PREPARE DESIGN CONCEPTS I Scbodul • and ""'" OF TASK. PERFORMING • e

DEVICES AND MOBILE e 'MJRKING SCALE MODELS EQUIPMENT

z -<

Fig. 1 Information Flow Plan

impacts. Soil Model 2 represents a site untouched by lava but near the now well-worn

craters formed during the early pre-mare lunar history. Soil Model 3 represents an

area near any of the numerous post-mare craters and has a rougher, more cohesive

surface than the other two soil models.

Table A

ASSUMED LUNAR SOIL MODELS

Characteristic Soil Model

1 2 3

Mean slope, deg 6 10 15

Maximum slope, deg 45 45 45

Surface bearing pressure, psi 10 to 100 10 to 100 100

Soil density, gm/cc 0.5to3.0 0. 5 to 3. 0 1. 5 to 3. 0

A radiation model was derived to account for cosmic ray primaries, travel through the

Van Allen belts , nuclear reactor emission, and solar flares. A meteoroid model was

also derived to account for sporadic and shower particles. The capabilities of man in

a shirt-sleeve and Apollo spacesuit environment were defined for operations on the

moon.

Finally, payload delivery restraints were defined in terms of Saturn V delivery system.

Personnel delivery is envisioned as being the same as now contemplated for Project

Apollo. Equipment and supplies would be delivered using the 22-ft-diameter LLV. A

value of 28, 000 lbm* was used as nominal delivery capability.

*In this report, lbm identifies pounds of mass, the fundamental unit of mass in the English system of units, while lb stands for pounds of force or weight. For most practical purposes on the earth, a pound of weight is numerically equivalent to a pound of mass.

4


Section 3

LESA BASE MODULES

A lunar base, as defined for this study, comprises the following major base modules:

basic shelter, lunar roving vehicle (LRV), maintenance shelter, nuclear power plant,

fuel-regeneration unit, and portable power supply.

Table B shows the composition of the LESA base models used in this study. Base

Model 1 consists of a single payload containing a shelter with built-in radiation and

meteoroid protection, LRV, thermal radiators, and solar-cell array. Base Model 2

uses the same equipment as Base Model 1, except that provisions are brought for six

men, and lunar soil is used for added meteoroid and radiation protection. Base Model

3 consists of numerous added modules including nuclear power plants, fuel-regeneration

units (to convert water to LH2 and L02 ), and a maintenance shelter. Base Model 4

adds another shelter, nuclear power plant, and LRV.

Table B

COMPOSITION OF BASE MODELS

Base Models Base Modules

1 2 3

Basic Shelter 1 1 2

Lunar Roving Vehicle 1 1 2

Maintenance Shelter 0 0 1

Nuclear Power Plant 0 0 3

Fuel-Regeneration Unit 0 0 2

Portable Power Supply 0 0 1

4

3

3

2

4

2

2

Eight concepts for basic shelter deployment were considered to examine the effects of

shelters being on or off the LLV, with lunar soil piled on the shelter or contained in a

caisson surrounding the structure, and with the LRV delivered above or below the

5

LOCKHEED MISSILES 8: SPACE COMPANY

shelter. Primary consideration for the LRV concept was given to a four-wheeled,

two-man vehicle of single-cab design suggested by Bendix. A separate 13,010-lbm

maintenance shelter payload concept, large enough to house the LRV, was developed

by LMSC.

Two 100-kwe nuclear power plant concepts were selected for study of deployment pro

cedures. The first was a 25, 000-lbm integral reactor-shielding concept proposed by

Westinghouse in its study of nuclear power plants for LESA. The second was a 14 ,30G-lbm

buried reactor concept suggested by LMSC, based on Westinghouse data, for an auto

matically deployed reactor buried in a previously excavated hole. To keep radiation

level down, it was determined that the integrally shielded concept should be deployed

at separation distances of 10, 000 ft, and the buried reactors should be sited at 2 ,500-ft

distances. The fuel-regeneration unit and portable power supply concepts were based

on modules suggested by Westinghouse in a study of engine and fuel systems for LESA.

Section 4

DEPLOYMENT OPERATIONS

In order to establish the effect of various deployment variables, the required operations

for the LESA base models were analyzed. Table C outlines the sequence of operation

envisioned for an evolutionary buildup to Base Model 4, as only evolutionary buildup to

each base model was considered.

4. 1 PREPARATORY OPERATIONS

A study of the advisability of carrying the booster nose shroud to the lunar surface for

added shielding and for functional use resulted in the conclusion that the shroud should

be jettisoned during ascent from the earth. It was concluded that the legs of the LLV

should be designed to provide gross leveling capability. Finally, it was concluded that

the shelter should be capable of rotating on the LLV to allow azimuth selection for

deployment and base operations, and a 320-lbm turntable was designed.

6


Table C

SEQUENCE OF DEPLOYMENT OPERATIONS

PREPARATORY UNLOADING SOIL TRANSPORTATION EMPLACEMENT DEACTIVATION

PAYLOAD LAUNCH (NOSE SHROUD EJECTION)

I LANDING AND LEVELING

AZIMUTH }ELECTION

BASE LRV UNL~ADING MODEL

I SHELTER A_fTIVATION LEVEL RADIATOR E~PlACEMENT

SOLAR AARAY EMPlACEMENT lF ANTENNA ERECTION

SHELTER U~LOADING (AT END 0[ 3 MO.)

r----f---- -- - . BASE DEACTIVATION - . - - -PAYLOAD LAUNCH, LANDING, CHECKOUT (SUPPLIES & FUEL)

SHELTER, ~ATOR, SOLAR ARRA":, ACTIVATION

UNLOAD SUPPLY TRANSPORT EQUIPMENT BASE UNLOAD SUPfues & FUEL

MODEL 2 TRANSPORT SUPPLIES & FUEL

LEVEL UNLOAD SOIL OPS. EQUIP.

SOIL CO~LECTION SOIL PREPARATION

SOIL TRANSPORTATION

SOIL PlACEMENT

BASE DEACTIVATION

- ·-f-· . . - -I-· . . -- - - - . '-· . (AT END~-

PAYLOAD LAUNCH, LANDING, CHECKOUT (SHELTEI</LRV, NUCLEAR POWER PLANTS, FRU, MAINT. SHELTER, SUPPLIES)

LRV UNLOADING

SHELTER, RAD~ATOR, SOLAR ARRAY ACTIVATION

UNLOAD SUPPLIES & FUEL

TRANSPORT SqJ>PLIES & FUEL

SHELTER U~LOADING UNLOAD SHELTER TRANSPORTER

UNLOAD PORTABLE POWER &ASE SUPPLY MODULE

MODEL PPS ER!CTION 3

LEVEL

(REPEAT TRANSPORT SHELTER

FOR COLLECT & PLACE SOIL BASE

MODEL SHELTER CO~NECTION •

LEVEL) TUNNEL ERE,fTION

EXCAVATE R~ACTOR HOLES

UNLOAD NUCLE.J. POWER PLANTS

EMPLA?E NPP'S

POWER liNE 2EPLOYMENT

UNLOAD FUEl REGEN. UNIT

TRANSP~RT FRU

EMPLtfF FRU

UNLOAD MAl NT. SHElTER

RAN SPORT M•AINT, SHELTER

EMPlACE ~NT. SHELTER

7


4. 2 UNLOADING OPERATIONS

A study of LRV and shelter arrangment showed that placement of the LRV above the

basic shelter resulted in lower deployment and mass delivery costs and resulted in

a lower vehicle center of gravity. The rotating A-frame with hoist shown in Figure 2

was selected as the LRV offloading method.

A semiautomatic tilting-rail method, shown in Figure 3, was selected after a study of

shelter offloading methods. The opposing davits, shown in Figure 4, were selected as

the most promising method for logistic payload unloading.

4. 3 SOIL OPERATIONS

Lunar soil is required to provide radiation and meteoroid protection for the Base

Model 2, 3, and 4 basic shelter concepts. In addition, it may be necessary to excavate

holes for burial of the nuclear reactors.

Cost point studies of the various soil operations resulted in selection of the backhoe

for soil collection, a screen to control particle size, the \!Se of a soil box attached to

an LRV trailer for soil transportation, and use of the A-frame with hoist for soil

placement. The sequence of these methods is shown in Figure 5. Using these

methods, a cost point study showed that, even for a shelter offloaded to the lunar

surface, piling soil around the shelter costs seven times as much as filling a 12-

in. -wide caisson. Thus, the caisson concept was selected.

4.4 TRANSPORTATION OPERATIONS

A study of methods to transport payloads across the lunar surface resulted in selection

of the bicycle with outrigger method for transporting large base modules (such as

shelters) and a trailer and LRV equipment carrier for transporting small packages.

8


b1l ·.-<

""'

9

LO

CK

HE

ED

M

ISS

ILE

S

&

SP

AC

E

CO

MP

AN

Y

Fig. 3 Selected Method for Shelter Unloading

...

Fig. 4 Selected Method for Logistics Payload Unloading

10

LOCKHEED MISSILES a SPACE COMPANY

a. b

0 d.

Fig. 5 Soil Operations Sequence

11


In the bicycle with outriggers method, as shown in Figure 6, two track-type propulsion

units, powered from the portable power supply towed by the LRV, provide the needed

mobility, while the outrigger wheels add stability. As shown in Figure 6, the LLV legs

can be used for outriggers if base modules are transported on the LLV. If the modules

are offloaded before moving, separate outriggers will be required.

Figure 7 shows the trailer and LRV equipment carrier. A davit similar to that shown

in Figure 4 can be used for a hoist on the trailer.

4.5 EMPLACEMENT AND ERECTION OPERATIONS

A cost point analysis showed that portable panels, emplaced on the lunar surface by

the crew, was the least costly method for deployment of solar-cell arrays and thermal

radiators. A study of low-frequency surface-to-surface communication antennas re

sulted in selection of a method for automatically deploying a 30-meter vertical monopole

from the shelter roof.

Section 5

DEPLOYMENT PROCEDURES

Using the selected methods for accomplishing the deployment operations (Section 4),

alternate procedures were derived to examine the effect of five major variables:

• Evolution patterns for the various base models

• Base modules left on their LLV's versus offloaded to the lunar surface

• Lunar surface and soil characteristics

• Base modules transported for optimum siting (shelters interconnected)

versus not transported and random siting

• Nuclear power plant above ground with integral shielding versus a buried

reactor

12


c'

• '-

... '-

"-"

""'

··---

Fig. 6 Selected Method for Transporting Large Base Modules

(...,

"-

... '--' Fig. 7

-·. .. .....__ 4.,J" "" <..J -~:.

Selected Methods for Transporting Small Packages 13


The full impact of these variables can be determined only after study of their effects

on base operation. In this study, only the impact on base deployment cost was con

sidered.

Seventeen procedures were developed and evaluated to examine the various effects of

the five major variables. A detailed task analysis was performed for each procedure

to determine required base modules, required deployment equipment, crew utilization,

(location and manhours), LRV usage, required power, and deployment time.

The results of this study are summarized in TableD, which shows the delivered mass,

deployment labor, and associated activity for each procedure. The operations associ

ated with each of the base evolution patterns can be obtained from Table C by noting

that Evolution Pattern A is establishment of the Base Model 1 level, Pattern B is

establishment of the Base Model 1 then Model 2 levels, Pattern C is the deployment

operations all the way through the first three base model levels , and Pattern D is

deployment from the beginning through the Base Model 4 level.

Section 6

DEPLOYMENT EQUIPMENT

The deployment operations and procedure analysis resulted in the conceptual design

of 15 pieces of deployment equipment. These designs are summarized in Table E.

Section 7

STRUCTURES DESIGN

Within the framework of Deployment Procedures, a brief study of structures was

performed. The definition of LESA base models established the basic requirements

for these structures (or base modules), and the analysis of deployment procedures

identified many detailed requirements for these structures.

14


r 0 ()

" I fTI fTI 0

~ (/) (/)

r fTI (/)

Q>

(/)

"U )> () fTI

()

0 ~ "U )> z -<

1-' 01

PROCEOORE NUMBER

PROCEDURE DESCRIPTION:

Bue Evolution Pattern

EvolutiOll GcMl (- Model No )

Bue Modulee ON or OFF LLV

Boll Model Number

Bitl11!1- Clwotered or Rmdom*

Nuclear Power PlaDt Shleldln«**

TOTAL DELIVERED MABII:

Bue Modulee (LBM)

Deploym- Equipment (LBM)

DEPLOYMENT LABOR (Man Houro):

c

OFF

1,2

c BR

u

c

OFF

1,2

c IS

TableD

DEPLOYMENT PROCEDURES COMPARISON

m

c

OFF

1,2

R

IS

IV

c

OFF

3

c BR

v

c 3

OFF

3

c IS

VI

c

OFF

3

R

IS

l'1ll

c

ON

1,2

c IS

VIU

c 3

ON

1,2

R

IS

IX

c

ON

3

c IS

X

c

ON

3

R

IS

XI

c

OFF

1,2

c IS

182,300 212.889 212.314 182,300 212,889 212,314 214,587 214,012 214,887 214,012 214,089

17,023 17,513 15,811 18,075 18,510 18,808 8,888 4,298 7,885 5,293 18,203

XII Xlll

A B

OFF ON

1,2,3 l,Z

Not Appllcable

XIV

D

• OFF

l,Z

c BR

XV

D

• OFF

1,2

c IS

XVJ

D

• OFF

1,1

R

IS

XVII

D

• ON

1,1

R

IS

28,1149

408

33,477 248,381 187,851 288,701 189,189

5,101 11,433 11,103 20,401 •• 978

In a Lunar 8utt

In Sbirt-111-.ee

zu 288 228 uo 358 313 228 tM 318 an 1n 17 74 aao 381 185 ua __!!!. ____£!! __ill ~ __lli ~ ~ ~ _.!!!. __!!! _!!! ___ 8 ----ill --...!!!. __.!.!! --...!!!! ---lli.

Total

LRV UBE:

Hour•

Mll-

Power u- (KWH)

Total Deployment Time (1111)

IIAiqulred No. ol Deploymeat llhlfta

899

354

102

888

371

53

74e

-189

917

371

47

•c • Bue Modulee cluotered In an O!ldmum otte lll'l'USement

857

294

185

751

319

38

R • Bue Modulea olted where !.-lila ..-m-......__

*"BR • Nuolea.r Power Plant llb1eldiDc ocbleved by buryiJic tbe reactor

1,845

842

354

3,113

8811

98

B • Nuclear Power Plant delivered with lllte!lral obleldl"'! for tile reoctor

1,157

557

273

2,201

585

M

1,083

1102

133

2,028

531

54

833

2N

188

818

319

u

1122

240

131

820

285

32

1,044

505

237

2,101

533

88

947

... 232

1,898

477

48

110

175

181

751

300

40

II

10

2

11

15

177

83

19

198

.. 13

119

471

137

1,1tl

503

et

1,015

481

158

l.JOO

511

83

871

-149

l,OJII

Ul

59

889

320

190

8JII

381

40

Table E

DEPLOYMENT EQUIPMENT SUMMARY

Max. Mass Power

No. Name Function (Ibm} ~w} Notes

r D-1 LRV Offloading Hoist Unload LRV, place soil, 540 0~03 80 min required for offloading 0 support crew elevator ()

D-2 LRV Equipment Carrier Carry small packages 82 - Limited to packages weighing 200 lb

" :r: (1, 200 Ibm) 111

D-3 Shelter Offloader Unload shelter from LLV, 1,807 0.1 1. 7 hr required for offloading, 111 0 rotate shelter on LLV semiautomatic operation

~ D-3a Buried Reactor Plant Unload nuclear power plant 1,530 0.1 Same as D-3. Lighter mass owing - Offloader with buried reactor concept to lighter load (I) (I) D-4 Materials Handling Unload cargo from LLV 232 1.3 Two per logistics LLV; limited to -r Hoist 1, 500 lb load (9, 000 Ibm) 111 ...... (I) Ol D-5 Logistics Trailer Carry equipment, supplies and 1,896 1.4 Generates 5 kw from built-in fuel cells. Ql soil; string power lines Carries 1, 500-lb max load (9, 000 Ibm)

(I) D-5a Logistics Vehicle Same as D-5 2,355 2.0 Carries 720 lb max. load (4, 300 Ibm) 1J

10-ft3 bucket; 3-min digging cycle )> D-6 Backhoe Soil collection, excavation 808 5.0 () 111 D-7 Soil Box Hold soil during handling 277 - Dumps soil on top of1 shelter () D-8 Soil Screen Eliminates large soil pieces 125 - Parallel bar design 0 ~ D-9a Shelter Transporter Move large modules with LLV 2,592 11.5 Handles 10, 000-lb load (60, 000 Ibm) 1J D-9b Shelter Transporter Move large modules without 1,702 4.3 Handles 5, 000-lb load (30, 000 Ibm) )>

z LLV -<

D-10 Rock Crusher Crush soil in Soil Model 3 1,121 5.0 Handles 10, 000 lbm;hr

D-11 Rotary Percussion Soil hole drilling, coring 100 1.8 Attaches to LRV via backhoe Drill

D-12 Personnel Elevator Crew ingress and egress 36 0.4 Attains speed of 60 ft/min

7. 1 BASIC SHELTER CONCEPT

A conceptual design of the shelter considered in this study is shown in Figure 8. It is

a six-man shelter using a 12-in.-wide caisson for soil shielding. The inner compart

ment, designated as living quarters, contains four bunks, personal hygiene facilities,

environment control system, food preparation and storage facilities, and a panel for

emergency shelter control and communication. The outer compartment, designated

as the working area or mission laboratory, is wrapped around the living compartment

(with a floor width of about 55 in. , wall-to-wall) and contains all the scientific mission

equipment. This equipment is attached to the inner wall to leave the outer wall clear

and directly accessible for repair in the event of a meteoroid puncture. Total free

volume of this shelter concept is 2, 570 cubic feet or about 430 cubic feet per man. Free

floor area is estimated at about 178 square feet or almost 30 square feet per man.

The airlock design is a departure from previous concepts of a cylindrical shell with

elliptical ends. This new design uses the pressure shells of the surrounding structure

for the air lock walls.

An onboard power system, consisting of a manually deployable solar-cell array supple

mented by fuel cells, was defined. A radioisotope thermoelectric generator (RTG) is

used to provide 100 watts of electric power during storage periods on the moon.

The life support system and fuel modules were defined for the shelter concept. A study

of the foundation concepts for offloaded payloads resulted in selection of a concept con

sisting of four baseplates connected to tubular screw jacks through ball joints.

A structural analysis considering meteoroid, radiation, and thermal-protection

requirements resulted in selection of a multiple-wall structure, using super insulation

and truss core panels. The resulting structure mass was estimated at 7, 131lbm.

17


r 0 () :A I JTI JTI 0

~ -(I) (I) -r JTI (I) ..... ~

00

(I)

1J )> () JTI

() 0 ~ 1J )> z -<

'=n u11f51fj~ /

'/I!BeJ?Toe_ ---------------l T CON[,(?/& Ci'!YIK'ONHfffu/PME}'I_I

-~

! 60?Et,l J!?Cf( (4J.c:

!li~(:TION A·~\

\

\ S/TNITRRY FJ?aLITIE$

y..:iti!'E£ !NSI!_I,AT!ON (!'! I /1 \ 5CIENTIFIC N/5'.5/0N

I 1\ Ct?UIPN.ENT (

I?Tc; A

L:... \

Foo~ P£cPI9PATiaY

~ \

$#/EL.D (/2")

Fig. 8 LESA Basic Shelter

cl--rAN'<A

-LOz

f?IK'LOC/r

_SCICNTIF/C .1'11S.5!0IY

1,Epu!PNENT

~- LoWE/? BVN/( (2)

/ /._______ UPPE'R lit/Nf( (2}

7. 2 PAYLOAD PACKAGING

Based on the deployment procedures analysis, an integrated set of payload packages

was determined. Table F summarizes the modules required for evolution to Base

Model 3, depending on whether the buried reactor nuclear power plant or the integrally

shielded nuclear power plant concept is considered.

Section 8

CONCLUSIONS AND RECOMMENDATIONS

This study has been successful in establishing apparent feasibility of the deployment

of all major systems now being contemplated for the LESA program. Of the total

deployment estimated cost, 85 to 90 percent can be attributed to the delivery charge

for the base modules themselves.

8.1 CONCLUSIONS

The major conclusions reached in this study are as follows:

(1) Deployment of the LESA base modules for any base model can be accomp

lished by three men and with power levels no higher than that provided by

the 25-kw portable power supply.

(2) Packaging of the basic shelter and LRV on the same payload results in

a mass estimated at about 30, 000 lbm, provided that the LRV is situated

above the shelter structure. Fully automatic LRV unloading, under earth

control, appears feasible using the method developed in this study.

(3) Use of built-in meteoroid protection plus the use of solar flare "storm

cellars", such as water blankets, for high-flux radiation protection results

in decreased deployment cost when compared with the use of soil shielding

for similar protection. Table G indicates that for Soil Model 1 or 2 there is

only a modest advantage, but that for Soil Model 3 there is pronounced

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Table F

LESA PAYLOAD PACKAGES

B ... Modoll Due Due

Model 1 Model a Buried Re10t:or ~ llblold-Reootor

No. ModWa A-1 B-1 F8-1 A-2 )(8-1 NPP-1 HPP-2 NPP-3 FRU-1 A-2 B-2 )18-1 NPP..1 NPP..2 NPP-3 FRU-1

8-1 Bulo l!be!Sor 7,131 '1,131 'J,lJl

8-2 RadlatiOil PrcUctioa- BM. 1 1,265

8-3 Reoupply Curler 2,000 2,000 2,000 2.000 2,000 2,000

11-4 ~e...U.r I, T&O t.no

8-6 !lbaltllrCGDMOicX' 61& 676

L-1 Bulo 1.11• EC8 3, '1''76 J,Tn 3,7'75

L-2 L8 a.ppl:r - - 2 6,800 5,808 6,800

L-3 Lll a.ppl:r - Buo s 5,580 7,181 7.181 6,680

L-C Lll a.ppl:r - Buo 4

L-6 ~· 8beher ECS 1,100 1.100

P-1 Bulo -r (FCUC) 1,,00 1,400 1.400

P-2 - UJdl (FCUC)- Duo Z 1,'780

P-3 -Ullli(FCUC)-BuoS 1,010 1,010

P-4 Portablo-lllwl1 6, 500 5.500

P-t. Nuoleu-~ 23.000 25,000 25.000

P-S Nuclear - Buried 14.300 14,300 14,300

P-t Power Dl.tributtOD. e,..tam. 1,423 860 2.800

C-1 Buio Commwdaatioll Urdt 342

C-2 Bulo ADteou>a 8ot 86

c-3 CoJDJDWIIoatioa. - Hue SM 238 238

C-4 ADteaou-Bue3aDd4 128 128

C-5 Emera:eDCy /Cbeckout 44 44 44

V-1 LRV- Dry 4,tl0 4.11t0 4,tl0 4,11t0 4,11t0

V-2 LRV l:spoodabloo 1,166 1.155 1.166 1. 155 1,156

F-1 Baaio Fuel Module 8,41'0 8,4'10 1,4'f0

F-2 lllpplemeaW Fuel - Duo 2 25,025

F-3 ~ememal Fuel - BaH J 1,616 3,550 5,125

F-4 lllpplom.-1 Fuel - Duo 4

F-5 MaiJJ&eD&DOe l!helter Fuel 2,110 2,180

F-t Fuel Rec.,.rattOD t1Dtt 28,000 28.000

D-1 LRV OllloodiJI( Holot 640 MD 640

D-2 LRV- Corrlor 82 82 82

D-3 llbelter otnoeder 1,80'7 1.630 },530 1,530 1,530 1,530 1,530 1,&30 1.&30 ], 530

D-lll Burlocl Nuoloor Olllooder 1,360 1,360 1,360

D-4 Malorlalo HaDdiiJI( Holoto - - 4M

D-6 Loclotlc Trailer 1,8H

D-llt Loc1oi1c Voblole

D-t Bocltboo 808

D-7 SoU !los 111

D-8 8oU Sene w D-a ~tor,....._...,. (8-1 + LLV)

D-a l!boltor TraDopc>rt.r (8-1 oaly) 1. 702 1,702

D-1 Rook cruber

D-1 1\ot.a.ry P.rouaaioD Drtll 100

D-t Po...-1 l:leYotor M M M

M-1 lllpplemeaW-- -- 1 400

M-2 ~meatal J:qul.,.....t-- I eoo

M-3 a.pplemesota' Equ.J.pmnt - Base 3 1,000 1,000

M-4 ~meoW J:qul_.a- B ... 4

X-1 Jlloaloa ~-- 1 8110

X-2 Jllollloo~--· 1,860

x-s :wtooloalllqlpon-s...a 130 130 1,480

X-4 llloo!oa _,. - Bue 4

X-6 Fuel~ .. ~

PAYIDAD TOT ALB 30,112 11,108 11,481 ~.014 .... ., 26,8111 2'7,144 2'7, TtO 2'1,&30 21,&64 21.&H ... 006 11,630 H.UO JI,UO Zf.UO

20


advantage. These advantages must be weighed against the operational

consideration of having the crew confined to water blankets during solar

flares. If soil is used, a 12-in. -wide expansible caisson is the preferred

concept.

Table G

EFFECT OF SOIL OPERATIONS ON DEPLOYMENT*

Radiation and Base Deploy. Total Total Total Total Meteoroid Proceed Protection No.

Module Equip. Labor Energy Time Cost

(Basic Shelter) Mass (Ibm) Mass (Ibm) (man-hr) (kw-hr) (hr) Points

Integral (no Soil XI 214,098 16,203 610 751 300 12,435 Shielding)

Soil Shielding II 212,889 17,513 746 917 371 12,628 (Soil Modell ,2)

Soil Shielding v 212,889 18,510 1,157 2, 201 585 13,318 (Soil Model 3)

*Base modules offloaded, clustered siting, integrally shielded nuclear power plants, Evolution Pattern C.

(4) Basic shelters should be clustered (transported into close proximity) and

inter connected with an environmentally controlled tunnel so that inter

shelter crew traffic can be in "shirt sleeves." The cost of clustering base

modules in an optimum siting arrangement is shown in Table H. The cost

of even limited inter-shelter crew transfer by crewmen in lunar suits ex

ceeds in less than 3 months the cost of clustering and interconnecting basic

shelters so as to enable this transfer to be accomplished in shirt sleeves.

(5) Nuclear power plant reactors should be buried below the lunar surface

rather than delivered with built-in radiation shielding provided the buried

reactor concept developed in this study can be satisfactorily activated and

operated. Table I shows the comparative advantage of the buried reactor

concept for Soil Models 1 or 2 and for Soil Model 3.

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Table H

EFFECT OF CLUSTERED SITE ARRANGEMENT

Proced. Total Mass Total Total Total Deployment* No. Delivered Labor Energy Cost

(lbm) (man-hr) (kw -hr) Points

Clustered, off LLV li 230,402 746 917 12,628

Random, off LL V III 228,125 657 751 12,367

Clustered, on LLV VII 221,475 633 818 12,022

Random, on LLV VIII 218,308 522 620 11,688

*Soil Model 1 or 2, integrally shielded reactor concept (power plants not transported), Evolution Pattern C

Table I

NUCLEAR POWER PLANT DEPLOYMENT COMPARISON*

Soil Reactor Proced. Total Mass Total Total Total Total

Model Concept No. Delivered Labor Energy Time Cost (lbm) (man-hr) (kw-hr) (hr) Points

1, 2 Buried I 199,323 699 888 379 11,043

1, 2 Integral shield II 230,402 746 917 371 12,628

3 Buried IV 200,375 1,645 8,113 868 12,529

3 Integral shield v 231,399 1,157 2,201 585 13,318

*Base modules offloaded, clustered siting, Evolution Pattern C

(6) Siting Base Model 1 in any of the soil models examined in this study can be

accomplished with little variation in cost. However, sites for all other base

models should be selected to avoid the rough surface areas corresponding

to Soil Model 3. Table J summarizes the adverse effect of Soil Model 3 on

deployment.

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Table J

EFFECT OF SOIL MODEL ON DEPLOYMENT

Soil Proced. Total Mass Total Total Total Deployment* Model No. Delivered Labor Energy Cost

(Ibm) (man-hr) (kw-hr) Points

Buried Reactors 1' 2 I 199,323 699 888 11' 043

3 IV 200,375 1, 645 3,113 12,529

Integrally Shielded 1, 2 II 230,402 746 917 12,628 Reactors 3 v 231,399 1,157 2,201 13,318

*Base modules offloaded, clustered siting, Evolution Pattern C

The conclusions presented here are insensitive to most of the assumptions made in

this report. The assumptions only made it possible to discuss deployment in quanti

tative terms. The one major exception is the set of assumptions related to character

istics of the lunar surface and soil. The density range, bearing pressure, hydrogen

content, sonic speed, cohesiveness, slope versus length, and subsurface temperature

are all key parameters. In general, values believed to be conservative were used in

assumptions made for any particular soil application. Thus a fairly large caisson,

large-sized transportation systems, and lengthly soil operations resulted.

8. 2 RECOMMENDATIONS

The following are the most important recommendations resulting from this study:

(1) Before further procedure analysis and optimization can proceed, a cost

effectiveness model, which relates the important lunar mission parameters,

should be developed. This means that more thought should be given to what

the important lunar mission parameters are. The cost point system used

in this report related such items as weight, deployment manhours, and

space-suit usage, but other parameters (such as launch -vehicle limitations,

exploration effectiveness, and maintenance costs), as well as time varia

tion of unit costs , should be factored into the model.

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(2) Tests should be conducted for each task suggested in this report to confirm

the feasibility of performing the task under one-sixth of earth's gravity and

space-suit limitations.

(3) A study of detailed maintenance requirements for the LRV and shelter

components should be made to determine the requirement for a separate

maintenance facility.

(4) A design study should be initiated to determine the feasibility of utilizing

the LLV landing legs to provide gross leveling capability.

(5) Intensive study of the lunar surface is already in progress. For deployment

equipment design, it is recommended that further data be obtained on the

following: Soil density, cohensiveness, bearing pressure versus depth,

hydrogen content, electromagnetic wave-carrying capability, surface details

(particularly slope versus slope length), and subsurface temperature.

(6) Tests should be conducted to determine operational problems associated

with the use of water bags for radiation protection. These tests should

determine physiological and psychological reactions of crew members to

confinement in the bags for periods up to several days in length.

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SUMMARY DIGEST DEPLOYMENT PROCEDURES · value of 28, 000 lbm* was used as nominal delivery...

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